Create aerospace_dynamics_simulator.py

core/aerospace/aerospace_dynamics_simulator.py

@@ -0,0 +1,81 @@
+import numpy as np
+from scipy.integrate import odeint
+
+class AerospaceDynamicsSimulator:
+    def __init__(self, vehicle_mass, vehicle_size, atmospheric_conditions):
+        self.vehicle_mass = vehicle_mass
+        self.vehicle_size = vehicle_size
+        self.atmospheric_conditions = atmospheric_conditions
+
+    def simulate(self, time_step, total_time):
+        # Define the equations of motion
+        def equations_of_motion(state, t):
+            # Calculate forces and moments
+            forces = self.calculate_forces(state)
+            moments = self.calculate_moments(state)
+
+            # Update state variables
+            state_dot = np.array([
+                state[1],
+                forces / self.vehicle_mass,
+                state[3],
+                moments / self.vehicle_mass
+            ])
+
+            return state_dot
+
+        # Initialize state variables
+        state0 = np.array([0, 0, 0, 0])
+
+        # Simulate the dynamics
+        state = odeint(equations_of_motion, state0, np.arange(0, total_time, time_step))
+
+        return state
+
+    def calculate_forces(self, state):
+        # Calculate aerodynamic forces
+        aerodynamic_forces = self.calculate_aerodynamic_forces(state)
+
+        # Calculate gravitational forces
+        gravitational_forces = self.calculate_gravitational_forces(state)
+
+        return aerodynamic_forces + gravitational_forces
+
+    def calculate_moments(self, state):
+        # Calculate aerodynamic moments
+        aerodynamic_moments = self.calculate_aerodynamic_moments(state)
+
+        return aerodynamic_moments
+
+    def calculate_aerodynamic_forces(self, state):
+        # Calculate air density
+        air_density = self.atmospheric_conditions.air_density(state[2])
+
+        # Calculate aerodynamic coefficients
+        aerodynamic_coefficients = self.vehicle_size.aerodynamic_coefficients(state[1])
+
+        # Calculate aerodynamic forces
+        aerodynamic_forces = 0.5 * air_density * aerodynamic_coefficients * state[1]**2
+
+        return aerodynamic_forces
+
+    def calculate_gravitational_forces(self, state):
+        # Calculate gravitational acceleration
+        gravitational_acceleration = self.atmospheric_conditions.gravitational_acceleration(state[2])
+
+        # Calculate gravitational forces
+        gravitational_forces = self.vehicle_mass * gravitational_acceleration
+
+        return gravitational_forces
+
+    def calculate_aerodynamic_moments(self, state):
+        # Calculate air density
+        air_density = self.atmospheric_conditions.air_density(state[2])
+
+        # Calculate aerodynamic coefficients
+        aerodynamic_coefficients = self.vehicle_size.aerodynamic_coefficients(state[1])
+
+        # Calculate aerodynamic moments
+        aerodynamic_moments = 0.5 * air_density * aerodynamic_coefficients * state[1]**2 * self.vehicle_size.length
+
+        return aerodynamic_moments